ES2343824B1 - PART OF COMPOSITE MATERIAL WITH ZONES OF DIFFERENT THICKNESS. - Google Patents
PART OF COMPOSITE MATERIAL WITH ZONES OF DIFFERENT THICKNESS. Download PDFInfo
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- ES2343824B1 ES2343824B1 ES200703401A ES200703401A ES2343824B1 ES 2343824 B1 ES2343824 B1 ES 2343824B1 ES 200703401 A ES200703401 A ES 200703401A ES 200703401 A ES200703401 A ES 200703401A ES 2343824 B1 ES2343824 B1 ES 2343824B1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
- B29D99/00—Subject matter not provided for in other groups of this subclass
- B29D99/0003—Producing profiled members, e.g. beams
- B29D99/0007—Producing profiled members, e.g. beams having a variable cross-section
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/17—Three or more coplanar interfitted sections with securing means
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/19—Sheets or webs edge spliced or joined
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/19—Sheets or webs edge spliced or joined
- Y10T428/192—Sheets or webs coplanar
- Y10T428/195—Beveled, stepped, or skived in thickness
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
- Y10T428/24174—Structurally defined web or sheet [e.g., overall dimension, etc.] including sheet or component perpendicular to plane of web or sheet
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
- Y10T428/24174—Structurally defined web or sheet [e.g., overall dimension, etc.] including sheet or component perpendicular to plane of web or sheet
- Y10T428/24182—Inward from edge of web or sheet
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
- Y10T428/24479—Structurally defined web or sheet [e.g., overall dimension, etc.] including variation in thickness
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Moulding By Coating Moulds (AREA)
- Laminated Bodies (AREA)
- Wrappers (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
- Woven Fabrics (AREA)
Abstract
Pieza de material compuesto con zonas de diferente espesor fabricada a partir de un apilado de telas de material compuesto que comprende al menos dos zonas adyacentes de diferente espesor (11, 15) y una zona de transición (13) entre ambas configurada con una sola pendiente (17), en la que el apilado está estructurado por: una primera y una cuarta sección formadas por al menos dos telas continuas (21, 21''; 29, 29'') que se extienden a lo largo de las tres zonas mencionadas (11, 13, 15); una segunda sección formada por uno o más paquetes de telas (23) simétricos y balanceados terminando en la zona de transición (13) intercalados entre una o más telas continuas (25); una tercera sección formada por un paquete de telas simétrico y balanceado (27) que se extiende a lo largo de las tres zonas mencionadas (11, 13, 15) intercalado entre una o más telas continuas (25).Piece of composite material with areas of different thickness manufactured from a stack of fabrics composite material comprising at least two adjacent areas of different thickness (11, 15) and a transition zone (13) between the two configured with a single slope (17), in which the stack is structured by: a first and a fourth section formed by minus two continuous fabrics (21, 21 ''; 29, 29 '') that extend to the along the three zones mentioned (11, 13, 15); A second section formed by one or more packages of symmetrical fabrics (23) and balanced ending in the transition zone (13) interspersed between one or more continuous fabrics (25); a third section formed for a symmetrical and balanced fabric package (27) that extends along the three mentioned zones (11, 13, 15) interspersed between one or more continuous fabrics (25).
Description
Pieza de material compuesto con zonas de diferente espesor.Piece of composite material with areas of different thickness
La presente invención se refiere a la estructura del apilado de una pieza de material compuesto con zonas de diferente espesor fabricada utilizando un proceso de conformado en caliente y, más en particular, a la estructura del apilado de una pieza con un perfil en forma de C con zonas de gran espesor.The present invention relates to the structure of stacking a piece of composite material with areas of different thickness manufactured using a forming process in hot and, more particularly, to the stacking structure of a piece with a C-shaped profile with thick areas.
En la industria aeronáutica son bien conocidos procesos de fabricación de piezas que comprenden básicamente una primera etapa de encintado y una segunda etapa de conformado en caliente.In the aviation industry they are well known parts manufacturing processes that basically comprise a first stage of curb and a second stage of forming in hot.
En la etapa de encintado se colocan en un molde/útil de forma apropiada capas de un material compuesto tal como el preimpregnado que es una mezcla de refuerzo fibroso y matriz polimérica susceptible de almacenamiento.In the curb stage they are placed in a mold / suitably useful layers of such a composite material as the prepreg which is a mixture of fibrous reinforcement and matrix polymer susceptible to storage.
Ese material se puede presentar en diversas formas y en particular en forma de tela. Para las matrices termoendurecibles la resina generalmente se cura parcialmente o se lleva mediante otro proceso a una viscosidad controlada, llamada B-etapa.That material can be presented in various shapes and in particular in the form of cloth. For the matrices thermosetting resin is usually partially cured or leads by another process to a controlled viscosity, called B-stage
Las telas de material compuesto no se colocan aleatoriamente sino que se disponen en cada zona en un número y con una orientación de su refuerzo fibroso, típicamente de fibra de carbono, determinados en función de la naturaleza y la magnitud de los esfuerzos que vaya a soportar la pieza en cada zona.Composite fabrics are not placed randomly but they are arranged in each zone in a number and with an orientation of its fibrous reinforcement, typically of fiber carbon, determined according to the nature and magnitude of the efforts that the piece will support in each zone.
Cada zona tiene pues una estructura propia de la disposición o apilado de las telas. La diferencia en espesor entre las diferentes zonas genera caídas de telas, lo que requiere disponer de un modelo de telas para cada pieza que establezca claramente como debe llevarse a cabo su disposición sobre el molde/útil durante el proceso de apilamiento. El resultado final es un laminado plano con zonas de distinto espesor.Each zone therefore has its own structure of the arrangement or stacking of fabrics. The difference in thickness between the different zones generate fabric falls, which requires have a fabric model for each piece you set clearly how your provision on the mold / useful during the stacking process. The end result is a flat laminate with areas of different thickness.
En la segunda etapa se lleva a cabo un proceso de conformado en caliente que consiste básicamente en situar el laminado plano resultante de la primera etapa sobre un útil o mandril con una geometría apropiada y, aplicar calor y vacío según un ciclo determinado, para que dicho laminado se adapte a la forma del útil.In the second stage a process is carried out hot forming which basically consists of placing the flat laminate resulting from the first stage on a tool or mandrel with an appropriate geometry and apply heat and vacuum according to a certain cycle, so that said laminate adapts to the shape of the useful.
Siguiendo procesos de ese tipo, en la industria aeronáutica se han fabricado diversas piezas de material compuesto en forma de C tales como largueros y costillas de cajón de torsión de estabilizadores horizontales de aviones siempre que las diferencias de espesor entre zonas adyacentes no fueran muy grandes ya que en otro caso se forman arrugas indeseables en los radios de las pendientes que unen estas zonas.Following such processes, in the industry A number of pieces of composite material have been manufactured C-shaped such as stringers and torsion drawer ribs of horizontal aircraft stabilizers provided that thickness differences between adjacent areas were not very large since in another case undesirable wrinkles form in the radii of the slopes that join these areas.
En la técnica conocida, las piezas con grandes diferencias de espesor entre dos zonas adyacentes, como por ejemplo un larguero del ala de un avión con una zona de anclaje del tren de aterrizaje que debe soportar una gran carga, ó bien se fabricaban en metal ó bien, si se fabricaban con materiales compuestos, se utilizaban angulares metálicos para unir almas y revestimientos planos de materiales compuestos.In the known technique, the pieces with large thickness differences between two adjacent areas, such as a stringer of the wing of an airplane with an anchor zone of the train of landing that must withstand a large load, or were manufactured in metal or, if manufactured with composite materials, they used metal angles to join souls and coatings plans of composite materials.
La presente invención está orientada a resolver el problema planteado por la limitación mencionada para fabricar piezas de material compuesto conformadas con diferencias de espesor grandes entre zonas adyacentes.The present invention is aimed at solving the problem posed by the limitation mentioned to manufacture composite pieces formed with thickness differences large between adjacent areas.
Un objeto de la presente invención es proporcionar una estructura de apilado que permita la fabricación de piezas de material compuesto con perfil en C conformadas en caliente con diferencias de espesor grandes entre zonas adyacentes.An object of the present invention is provide a stacking structure that allows the manufacture of Hot-formed C-shaped composite parts with large thickness differences between adjacent areas.
Otro objeto de la presente invención es proporcionar una estructura de apilado que permita evitar las arrugas en las partes curvas de zonas adyacentes con diferencias de espesor grande de piezas de material compuesto conformadas en caliente.Another object of the present invention is provide a stacking structure that avoids wrinkles in the curved parts of adjacent areas with differences of large thickness of composite parts formed in hot.
Estos y otros objetos se consiguen mediante piezas fabricadas a partir de un apilado de telas de material compuesto que comprenden al menos dos zonas adyacentes de diferente espesor y una zona de transición entre ambas configurada con una sola pendiente, comprendiendo la estructura del apilado, desde la cara interior a la exterior de la pieza:These and other objects are achieved by parts made from a stack of material fabrics compound comprising at least two adjacent areas of different thickness and a transition zone between both configured with a single slope, comprising the structure of the stack, from the inner side to the outside of the piece:
- Una primera sección formada por al menos dos telas continuas que se extienden a lo largo de las tres zonas mencionadas.- A first section consisting of at least two continuous fabrics that extend along the three zones mentioned.
- Una segunda sección formada por uno o más paquetes de telas simétricos y balanceados intercalados entre una o más telas continuas que se extienden a lo largo de las tres zonas mencionadas, extendiéndose dichos paquetes de telas a lo largo de la zona de mayor espesor y terminando en la zona de transición de manera que ésta tenga una pendiente continua.- A second section consisting of one or more symmetrical and balanced fabric packages interspersed between one or more continuous fabrics that extend throughout the three zones mentioned, said fabric packages extending along the thicker area and ending in the transition zone of so that it has a continuous slope.
- Una tercera sección formada por un paquete de telas simétrico y balanceado que se extiende a lo largo de las tres zonas mencionadas intercalado entre una o más telas continuas que se extienden a lo largo de las tres zonas mencionadas.- A third section consisting of a package of symmetrical and balanced fabrics that extends throughout the three mentioned areas sandwiched between one or more continuous fabrics that They extend along the three mentioned zones.
- Una cuarta sección formada por al menos dos telas continuas que se extienden a lo largo de las tres zonas mencionadas.- A fourth section consisting of at least two continuous fabrics that extend along the three zones mentioned.
Otras características y ventajas de la presente invención se desprenderán de la descripción detallada que sigue de una realización ilustrativa de su objeto en relación con las figuras que le acompañan.Other features and advantages of this invention will follow from the detailed description that follows from an illustrative embodiment of its object in relation to the figures that accompany him.
La Figura 1 es una vista esquemática en perspectiva de un larguero con un perfil en forma C con zonas de distinto espesor.Figure 1 is a schematic view in perspective of a stringer with a C-shaped profile with areas of different thickness
La Figura 2 es una vista esquemática en sección transversal del larguero de la Figura 1.Figure 2 is a schematic sectional view. cross section of the crossbar of Figure 1.
La Figura 3 es una vista en sección transversal de una estructura de apilado según una primera realización de la presente invención.Figure 3 is a cross-sectional view. of a stacking structure according to a first embodiment of the present invention
La Figura 4 es una vista en sección transversal de una estructura de apilado según una segunda realización de la presente invención.Figure 4 is a cross-sectional view. of a stacking structure according to a second embodiment of the present invention
La presente invención resulta aplicable a una pieza con perfil en forma de C, como el larguero 1, que tiene zonas 3, 3', 3'' con gran diferencia de espesor entre ellas que determinan la existencia de las pendientes 5, 5' en las zonas de transición entre ellas.The present invention is applicable to a piece with C-shaped profile, such as stringer 1, which has zones 3, 3 ', 3' 'with great thickness difference between them that determine the existence of slopes 5, 5 'in transition zones between them.
En la fabricación de piezas de material compuesto de ese tipo mediante procesos de conformado en caliente a partir de laminados planos realizados con una estructura de apilado convencional, siguiendo los modelos típicos de telas con caídas en las zonas donde se producen saltos de espesor, cuando las diferencias de espesor entre las zonas 3, 3', 3'' superan ciertos límites, se producen arrugas 7 en las partes curvas 9 de las pendientes 5, 5' que la hacen inviable.In the manufacture of material parts compound of that type by hot forming processes to from flat laminates made with a stacking structure conventional, following the typical models of fabrics with falls in the areas where thick jumps occur, when thickness differences between zones 3, 3 ', 3' 'exceed certain limits, wrinkles 7 occur in curved parts 9 of the 5, 5 'earrings that make it unfeasible.
Para hacer viable la fabricación de ese tipo de piezas y satisfacer consiguientemente una demanda de la industria aeronáutica orientada cada vez más a la utilización masiva de materiales compuestos, los inventores han encontrado una estructura del apilado que evita la formación de dichas arrugas y que pasamos a describir en dos realizaciones de la invención.To make viable the manufacture of that type of parts and consequently meet an industry demand aeronautics oriented more and more to the massive use of composite materials, the inventors have found a structure of the stack that prevents the formation of these wrinkles and that we pass to describe in two embodiments of the invention.
Siguiendo la realización mostrada en la Figura 3 puede verse la estructura del apilado en la parte de una pieza entre dos zonas adyacentes 11, 15 de diferente espesor con una zona de transición 13 entre ambas de pendiente continua 17.Following the embodiment shown in Figure 3 the structure of the stack can be seen in the part of a piece between two adjacent zones 11, 15 of different thickness with an area of transition 13 between both of continuous slope 17.
La existencia de una única pendiente 17 en la zona de transición 13 facilita la definición y ejecución del utillaje necesario para el conformado en caliente de la pieza y del utillaje necesario para el curado definitivo.The existence of a single pending 17 in the transition zone 13 facilitates the definition and execution of necessary tools for hot forming of the part and the necessary tools for the definitive cure.
Desde su cara interior (a través de la cual se apoyará en el útil empleado durante el proceso de conformado en caliente) a su cara exterior, la estructura del apilado comprende las siguientes secciones:From its inner face (through which it will support the tool used during the forming process in hot) to its outer face, the stack structure comprises the following sections:
- Una primera sección formada por al menos dos telas continuas 21, 21' a lo largo de las tres zonas mencionadas 11, 13, 15.- A first section consisting of at least two continuous fabrics 21, 21 'along the three zones mentioned 11, 13, 15.
- Una segunda sección formada por uno o más
paquetes de telas 23 simétricos (es decir que presentan total
simetría de orientaciones respecto a la línea media del laminado) y
balanceados (es decir que tienen el mismo número de capas de +45° y
de -45°) intercalados entre una o más telas continuas 25 que se
extienden a lo largo de las tres zonas mencionadas 11, 13, 15.
Dichos paquetes 23 se extienden a lo largo de la zona de mayor
espesor 11 y terminan en la zona de transición 13 de manera que ésta
tenga una pendiente continua 17. El número de telas de los paquetes
23 depende de la dimensión del salto de espesor entre la zona 11 y
la zona 15 y del espacio disponible para
resolverlo.- A second section formed by one or more packages of symmetrical fabrics 23 (that is to say they have total symmetry of orientations with respect to the midline of the laminate) and balanced (that is to say they have the same number of layers of + 45 ° and - 45 °) sandwiched between one or more continuous fabrics 25 that extend along the three mentioned zones 11, 13, 15. Said packages 23 extend along the thickest zone 11 and end in the transition zone 13 so that it has a continuous slope 17. The number of fabrics in packages 23 depends on the size of the thickness jump between zone 11 and zone 15 and the space available for
solve.
- Una tercera sección formada por un paquete de telas simétrico y balanceado 27 que se extiende a lo largo de las tres zonas mencionadas 11, 13, 15 intercalado entre una o más telas continuas 25 que también se extienden a lo largo de las tres zonas mencionadas 11, 13, 15. En la realización ilustrada en la Figura 3, el paquete de telas 27 incluye dos zonas de diferente espesor que determinan una pendiente 31 entre ellas. Se considera que el límite máximo de la diferencia de espesor de esas dos zonas del paquete de telas 27 es de 2 mm.- A third section consisting of a package of symmetrical and balanced fabrics 27 that runs along the three mentioned zones 11, 13, 15 interspersed between one or more fabrics continuous 25 that also extend along the three zones mentioned 11, 13, 15. In the embodiment illustrated in Figure 3, the fabric pack 27 includes two zones of different thickness that determine a slope 31 between them. The limit is considered maximum of the difference in thickness of those two zones of the package of fabrics 27 is 2 mm.
- Una cuarta sección formada por al menos dos telas continuas 29, 29' que se extienden a lo largo de las tres zonas mencionadas 11, 13, 15.- A fourth section consisting of at least two continuous fabrics 29, 29 'that extend along the three mentioned areas 11, 13, 15.
Esta estructura del apilado combina zonas 33 de apilado convencional, que podemos denominar como zonas con telas completamente alternadas, donde el apilado es completamente simétrico y balanceado, con zonas 35 de un apilado novedoso, que podemos denominar zonas con telas parcialmente alternadas, en las que los paquetes 23 son internamente simétricos y balanceados, pero que originan que en el laminado completo, es decir en el conjunto de las zonas 33 y 35, sólo se cumple con la condición de balanceado.This stack structure combines zones 33 of conventional stacking, which we can call areas with fabrics completely alternated, where the stack is completely symmetrical and balanced, with zones 35 of a novel stack, which we can denominate zones with partially alternated fabrics, in the that packages 23 are internally symmetric and balanced, but that originate in the complete laminate, that is in the set of Zones 33 and 35, only the condition of balanced.
Esta estructura del apilado evita las arrugas ya que permite situar las capas más sensibles a la producción de arrugas dentro de la zona 33 de apilado convencional y las menos sensibles en la zona 35 de apilado novedoso bien en los paquetes de telas 23 o en las telas 25 que los envuelven.This stack structure prevents wrinkles and which allows to locate the most sensitive layers to the production of wrinkles within zone 33 of conventional stacking and the least sensitive in zone 35 stacking novelty well in packages fabrics 23 or in fabrics 25 that wrap them.
En la realización de la invención mostrada en la Figura 4 la única diferencia de la estructura del apilado con la de la Figura 3 es que la conformación de la pendiente continua 17 de la zona de transición 13 se obtiene combinando dos caídas 31, 31' del paquete de telas 27 simétrico y balanceado con las caídas correspondientes a los paquetes 23 de la zona 35 parcialmente intercalada. El limite máximo de las diferencia de espesor en las zonas del paquete 27 donde se producen las caídas 31, 31' es de 2 mm al igual que en el caso anterior.In the embodiment of the invention shown in the Figure 4 the only difference of the stack structure with that of Figure 3 is that the conformation of the continuous slope 17 of the transition zone 13 is obtained by combining two falls 31, 31 'of the symmetrical and balanced fabric pack 27 with falls corresponding to packages 23 of zone 35 partially interspersed The maximum limit of thickness differences in areas of package 27 where falls occur 31, 31 'is 2 mm as in the previous case.
En la realización preferente que acabamos de describir pueden introducirse aquellas modificaciones comprendidas dentro del alcance definido por las siguientes reivindicaciones.In the preferred embodiment we have just describe those modifications included within the scope defined by the following claims.
Claims (6)
Priority Applications (8)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| ES200703401A ES2343824B1 (en) | 2007-12-21 | 2007-12-21 | PART OF COMPOSITE MATERIAL WITH ZONES OF DIFFERENT THICKNESS. |
| US12/070,906 US7722944B2 (en) | 2007-12-21 | 2008-02-21 | Piece made of composite material with areas of different thickness |
| RU2010130565/05A RU2010130565A (en) | 2007-12-21 | 2008-12-19 | ELEMENT EXECUTED FROM COMPOSITE MATERIAL, WITH AREAS OF DIFFERENT THICKNESS |
| BRPI0821786-6A BRPI0821786A2 (en) | 2007-12-21 | 2008-12-19 | Part made of composite material with different thickness areas |
| EP08864018.0A EP2234793B1 (en) | 2007-12-21 | 2008-12-19 | Piece made of composite material with areas of different thickness |
| CA2710071A CA2710071A1 (en) | 2007-12-21 | 2008-12-19 | Piece made of composite material with areas of different thickness |
| PCT/EP2008/067979 WO2009080735A2 (en) | 2007-12-21 | 2008-12-19 | Piece made of composite material with areas of different thickness |
| ES08864018.0T ES2611942T3 (en) | 2007-12-21 | 2008-12-19 | Composite piece with zones of different thickness |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| ES200703401A ES2343824B1 (en) | 2007-12-21 | 2007-12-21 | PART OF COMPOSITE MATERIAL WITH ZONES OF DIFFERENT THICKNESS. |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| ES2343824A1 ES2343824A1 (en) | 2010-08-10 |
| ES2343824B1 true ES2343824B1 (en) | 2011-07-18 |
Family
ID=40717106
Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| ES200703401A Expired - Fee Related ES2343824B1 (en) | 2007-12-21 | 2007-12-21 | PART OF COMPOSITE MATERIAL WITH ZONES OF DIFFERENT THICKNESS. |
| ES08864018.0T Active ES2611942T3 (en) | 2007-12-21 | 2008-12-19 | Composite piece with zones of different thickness |
Family Applications After (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| ES08864018.0T Active ES2611942T3 (en) | 2007-12-21 | 2008-12-19 | Composite piece with zones of different thickness |
Country Status (7)
| Country | Link |
|---|---|
| US (1) | US7722944B2 (en) |
| EP (1) | EP2234793B1 (en) |
| BR (1) | BRPI0821786A2 (en) |
| CA (1) | CA2710071A1 (en) |
| ES (2) | ES2343824B1 (en) |
| RU (1) | RU2010130565A (en) |
| WO (1) | WO2009080735A2 (en) |
Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| ES2384920B1 (en) * | 2009-03-31 | 2013-05-21 | Airbus Operations, S.L. | Piece of material with a ramp between two zones. |
| ES2383863B1 (en) | 2009-05-06 | 2013-06-10 | Airbus Operations, S.L. | COMPOSITE MATERIAL PART WITH GREAT THICKNESS CHANGE. |
| GB0912015D0 (en) * | 2009-07-10 | 2009-08-19 | Airbus Operations Ltd | Stringer |
| GB2533369A (en) * | 2014-12-18 | 2016-06-22 | Airbus Operations Ltd | Method of forming a Laminar composite structure |
| US11446884B2 (en) | 2018-10-29 | 2022-09-20 | Airbus Operations Gmbh | Process for producing a component which is two-dimensional in regions from a fibre composite material |
| US10919260B2 (en) * | 2019-05-09 | 2021-02-16 | The Boeing Company | Composite structure having a variable gage and methods for forming a composite structure having a variable gage |
| US10913215B2 (en) * | 2019-05-09 | 2021-02-09 | The Boeing Company | Composite structure having a variable gage and methods for forming a composite structure having a variable gage |
| US10919256B2 (en) * | 2019-05-09 | 2021-02-16 | The Boeing Company | Composite structure having a variable gage and methods for forming a composite structure having a variable gage |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE69910174T3 (en) * | 1999-04-07 | 2012-03-08 | Mcdonnell Douglas Corp. | Knowledge-based design optimization process for composites and system for it |
| US7238409B1 (en) * | 2002-05-23 | 2007-07-03 | Rohr, Inc. | Structural element with rib-receiving member |
| EP1547756A1 (en) * | 2003-12-24 | 2005-06-29 | Airbus UK Limited | Method of manufacturing aircraft components |
| EP1840775A1 (en) * | 2006-03-31 | 2007-10-03 | Airbus Espana, S.L. | Computer-aided method of obtaining a ply model of composite component |
-
2007
- 2007-12-21 ES ES200703401A patent/ES2343824B1/en not_active Expired - Fee Related
-
2008
- 2008-02-21 US US12/070,906 patent/US7722944B2/en not_active Expired - Fee Related
- 2008-12-19 CA CA2710071A patent/CA2710071A1/en not_active Abandoned
- 2008-12-19 WO PCT/EP2008/067979 patent/WO2009080735A2/en active Application Filing
- 2008-12-19 ES ES08864018.0T patent/ES2611942T3/en active Active
- 2008-12-19 EP EP08864018.0A patent/EP2234793B1/en not_active Not-in-force
- 2008-12-19 BR BRPI0821786-6A patent/BRPI0821786A2/en not_active IP Right Cessation
- 2008-12-19 RU RU2010130565/05A patent/RU2010130565A/en not_active Application Discontinuation
Non-Patent Citations (1)
| Title |
|---|
| NIU, Michael C. Y. Composite Airframe Structures. 3$^{a}$ ed. Hong Kong: Hong Kong Conmilit Press Limited, 2000, ISBN 962-7128-06-6; páginas 189-199, 443, 445. En particular, página 189, 4 últimas líneas; página 193, 12 primeras líneas; página 198 completa; figuras 4.2.8 y 4.2.17; página 443, en particular las 3 últimas líneas; página 445, en particular figura 7.5.12. * |
Also Published As
| Publication number | Publication date |
|---|---|
| US20090162613A1 (en) | 2009-06-25 |
| CA2710071A1 (en) | 2009-07-02 |
| BRPI0821786A2 (en) | 2015-06-16 |
| US7722944B2 (en) | 2010-05-25 |
| WO2009080735A2 (en) | 2009-07-02 |
| ES2611942T3 (en) | 2017-05-11 |
| EP2234793A2 (en) | 2010-10-06 |
| ES2343824A1 (en) | 2010-08-10 |
| EP2234793B1 (en) | 2016-10-19 |
| RU2010130565A (en) | 2012-01-27 |
| WO2009080735A3 (en) | 2009-08-27 |
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